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Open AccessJournal ArticleDOI

A Numerical Method for Calculating the Trailing Vortex System behind a Swept Wing at Low Speed

D. J. Butter, +1 more
- 01 Aug 1971 - 
- Vol. 75, Iss: 728, pp 564-568
TLDR
In this article, a method is presented for the prediction of the spatial distribution of the trailing vorticity during the rolling up process, thus giving the overall downwash field behind the wing.
Abstract: 
A wing of finite span in flight generates trailing vorticity which “rolls up” into two “discrete” vortices. During the rolling up process the trailing vorticity is displaced vertically downward (assuming that the aircraft is in horizontal flight) under the influence of the wing circulation and the self-induced downwash velocities. In this note a method is presented for the prediction of the spatial distribution of the trailing vorticity during the rolling up process, thus giving the overall downwash field behind the wing.

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Citations
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A subvortex technique for the close approach to a discretized vortex sheet

Brian Maskew
TL;DR: In this paper, a sub-vortex technique was used to calculate velocities at arbitrary points, not just at midpoints, between the vortices in a cambered Joukowski airfoil.
Journal ArticleDOI

Induced Drag Minimization: A Variational Approach Using the Acceleration Potential

Luciano Demasi
- 01 May 2006 - 
TL;DR: In this paper, a method of predicting the minimum induced drag conditions in conventional or innovative lifting systems is presented, based on lifting-line theories and the small perturbation acceleration potential, and the optimal conditions are formulated using the Euler-Lagrange integral equation subject to the conditions of fixed total lifting force and wing span.
Journal ArticleDOI

The rolling up of a trailing vortex sheet

R R Clements, +1 more
- 01 Jan 1973 - 
TL;DR: The early design charts of Silvertstein et al gave downwash angles for a variety of flapped and unflapped aerofoils by considering the trailing vortex sheet to be composed of discrete line vortices but ignored the rolling up process as discussed by the authors.
Journal ArticleDOI

Interference between tanker wing wake with roll-up and receiver aircraft

A. W. Bloy, +1 more
- 01 Sep 1994 - 

A quadrilateral vortex method applied to configurations with high circulation

Brian Maskew
TL;DR: A quadrilateral vortex-lattice method is briefly described for calculating the potential flow aerodynamic characteristics of high-lift configurations in this paper, where the deformation of force-free wakes, including wakes from side edges, is calculated.
References
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Journal ArticleDOI

Aufwicklung einer unstabilen Unstetigkeitsfläche

H. Kaden

Downwash and Wake Behind Plain and Flapped Airfoils

Abe Silverstein, +2 more
TL;DR: In this paper, a detailed study was made of the errors involved in applying lifting-line theory, such as the effects of a finite wing chord, the rolling-up of the trailing vortex sheet, and the wake.

Design Charts for Predicting Downwash Angles and Wake Characteristics Behind Plain and Flapped Wings

Abe Silverstein, +1 more
TL;DR: In this paper, the downwash angles and the wake characteristics for power-off conditions behind plain and flapped wings of the types used in modern design practice are predicted for the case of elliptical wings and wings of taper ratios 1, 2, 3, and 5, with aspect ratios of 6, 9, and 12, having flaps covering 0, 40, 70, and 100 percent of the span.
Journal ArticleDOI

The rolling up of a trailing vortex sheet

R R Clements, +1 more
- 01 Jan 1973 - 
TL;DR: The early design charts of Silvertstein et al gave downwash angles for a variety of flapped and unflapped aerofoils by considering the trailing vortex sheet to be composed of discrete line vortices but ignored the rolling up process as discussed by the authors.

A Theoretical Investigation of Vortex-Sheet Deformation Behind a Highly Loaded Wing and Its Effect on Lift

Clarence D. Cone
TL;DR: In this article, the induced velocities of the wake limit the maximum lift coefficient to a value of 1.94 times the wing aspect ratio, for aspect ratios equal to or less than 6.5.